GOE 416A AIRFOIL (goe416a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 416A AIRFOIL (goe416a-il) Reynolds number: 200,000 Max Cl/Cd: 61.35 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe416a-il-200000.txt Download as CSV file: xf-goe416a-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 416A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4555 0.13348 0.13010 -0.0026 1.0000 0.0437
-12.500 -0.4580 0.12984 0.12648 -0.0043 1.0000 0.0458
-12.250 -0.4666 0.12526 0.12192 -0.0074 1.0000 0.0477
-6.000 -0.5366 0.02447 0.01724 -0.0334 1.0000 0.0446
-5.750 -0.5103 0.02359 0.01602 -0.0314 1.0000 0.0365
-5.500 -0.4883 0.02174 0.01410 -0.0301 1.0000 0.0362
-5.250 -0.4665 0.02047 0.01275 -0.0288 1.0000 0.0364
-5.000 -0.4454 0.01888 0.01117 -0.0274 1.0000 0.0354
-4.750 -0.4246 0.01768 0.00997 -0.0261 1.0000 0.0348
-4.500 -0.4038 0.01668 0.00897 -0.0249 1.0000 0.0347
-4.250 -0.3823 0.01581 0.00808 -0.0240 1.0000 0.0351
-4.000 -0.3599 0.01506 0.00728 -0.0234 1.0000 0.0359
-3.750 -0.3365 0.01441 0.00652 -0.0231 1.0000 0.0383
-3.500 -0.3122 0.01381 0.00579 -0.0229 1.0000 0.0422
-3.250 -0.2741 0.01337 0.00521 -0.0252 0.9963 0.0483
-3.000 -0.2345 0.01118 0.00479 -0.0294 0.9922 0.4594
-2.750 -0.1909 0.01182 0.00544 -0.0322 0.9843 0.5238
-2.500 -0.1505 0.01219 0.00581 -0.0344 0.9759 0.5513
-2.250 -0.1073 0.01242 0.00612 -0.0371 0.9701 0.5720
-2.000 -0.0690 0.01260 0.00631 -0.0389 0.9609 0.5919
-1.750 -0.0286 0.01249 0.00622 -0.0412 0.9531 0.6004
-1.500 0.0089 0.01236 0.00600 -0.0431 0.9422 0.6072
-1.250 0.0421 0.01214 0.00576 -0.0439 0.9286 0.6108
-1.000 0.0727 0.01196 0.00556 -0.0440 0.9134 0.6142
-0.750 0.1011 0.01182 0.00535 -0.0437 0.8969 0.6180
-0.500 0.1277 0.01172 0.00515 -0.0432 0.8773 0.6218
-0.250 0.1537 0.01156 0.00497 -0.0424 0.8577 0.6245
0.000 0.1798 0.01145 0.00481 -0.0416 0.8381 0.6278
0.250 0.2063 0.01138 0.00468 -0.0411 0.8166 0.6316
0.500 0.2333 0.01134 0.00454 -0.0406 0.7968 0.6353
0.750 0.2602 0.01127 0.00443 -0.0402 0.7752 0.6384
1.000 0.2870 0.01124 0.00435 -0.0398 0.7542 0.6420
1.250 0.3142 0.01126 0.00431 -0.0395 0.7327 0.6461
1.500 0.3416 0.01131 0.00425 -0.0392 0.7113 0.6502
1.750 0.3686 0.01133 0.00423 -0.0389 0.6890 0.6537
2.000 0.3956 0.01139 0.00425 -0.0386 0.6681 0.6581
2.250 0.4231 0.01150 0.00431 -0.0385 0.6486 0.6632
2.500 0.4506 0.01157 0.00438 -0.0384 0.6294 0.6678
2.750 0.4779 0.01166 0.00448 -0.0383 0.6114 0.6728
3.000 0.5055 0.01179 0.00459 -0.0382 0.5939 0.6786
3.250 0.5327 0.01185 0.00470 -0.0381 0.5752 0.6843
3.500 0.5600 0.01192 0.00482 -0.0379 0.5554 0.6917
3.750 0.5867 0.01199 0.00491 -0.0377 0.5354 0.6990
4.000 0.6139 0.01206 0.00506 -0.0376 0.5139 0.7081
4.250 0.6403 0.01214 0.00520 -0.0372 0.4934 0.7177
4.500 0.6664 0.01225 0.00538 -0.0369 0.4703 0.7300
4.750 0.6916 0.01239 0.00558 -0.0364 0.4430 0.7468
5.000 0.7155 0.01252 0.00580 -0.0356 0.4128 0.7728
5.250 0.7374 0.01252 0.00603 -0.0342 0.3841 0.8357
5.500 0.7671 0.01257 0.00622 -0.0346 0.3505 1.0000
5.750 0.7939 0.01294 0.00652 -0.0347 0.3176 1.0000
6.000 0.8196 0.01340 0.00686 -0.0345 0.2838 1.0000
6.250 0.8438 0.01403 0.00732 -0.0343 0.2513 1.0000
6.500 0.8674 0.01473 0.00789 -0.0339 0.2158 1.0000
6.750 0.8908 0.01544 0.00844 -0.0336 0.1620 1.0000
7.000 0.9101 0.01679 0.00937 -0.0328 0.1032 1.0000
7.250 0.9300 0.01807 0.01051 -0.0319 0.0755 1.0000
7.500 0.9491 0.01941 0.01177 -0.0309 0.0570 1.0000
7.750 0.9659 0.02104 0.01340 -0.0295 0.0464 1.0000
8.000 0.9849 0.02232 0.01472 -0.0284 0.0397 1.0000
8.250 1.0018 0.02403 0.01649 -0.0270 0.0353 1.0000
8.500 1.0213 0.02543 0.01802 -0.0258 0.0323 1.0000
8.750 1.0399 0.02702 0.01964 -0.0247 0.0301 1.0000
9.000 1.0565 0.03026 0.02294 -0.0235 0.0281 1.0000
9.250 1.0757 0.03158 0.02451 -0.0223 0.0267 1.0000
9.500 1.0934 0.03331 0.02648 -0.0211 0.0251 1.0000
9.750 1.1092 0.03568 0.02912 -0.0198 0.0243 1.0000
10.000 1.1221 0.03832 0.03205 -0.0183 0.0236 1.0000
10.250 1.1313 0.04129 0.03534 -0.0165 0.0233 1.0000
10.500 1.1348 0.04467 0.03909 -0.0144 0.0232 1.0000
10.750 1.1307 0.04846 0.04328 -0.0120 0.0233 1.0000
11.000 1.1174 0.05224 0.04742 -0.0090 0.0236 1.0000
11.250 1.0998 0.05625 0.05175 -0.0068 0.0239 1.0000
11.500 1.0801 0.06073 0.05649 -0.0060 0.0242 1.0000
11.750 1.0588 0.06582 0.06183 -0.0069 0.0245 1.0000
12.000 1.0364 0.07171 0.06795 -0.0093 0.0249 1.0000
12.250 1.0130 0.07854 0.07498 -0.0133 0.0252 1.0000
12.500 0.9887 0.08634 0.08295 -0.0185 0.0255 1.0000
12.750 0.9629 0.09540 0.09216 -0.0250 0.0258 1.0000
13.000 0.9356 0.10584 0.10271 -0.0324 0.0262 1.0000
13.250 0.9071 0.11774 0.11468 -0.0401 0.0268 1.0000
13.500 0.8861 0.12794 0.12487 -0.0451 0.0277 1.0000
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Polar data table (+)
Polar graphs
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